FIELD: gas turbine engines.
SUBSTANCE: invention relates to gas turbine engines. The gas turbine engine contains an inlet device, a compressor, a turbine, an annular combustion chamber with nozzles, a flame tube, an annular gap between the outer casing of the flame tube and the combustion chamber housing, which communicates with the cavity of the flame tube, the flame tube is provided with holes for supplying cooling air. Holes for supplying cooling air are made with flanges; through the longitudinal axis of the annular combustion chamber.
EFFECT: increasing the efficiency of the engine and reducing the circumferential unevenness of the temperature field at the outlet of the combustion chamber.
1 cl, 6 dwg
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